Projectile system with environmental hazard sensing

ABSTRACT

In one aspect, a modular air sampling system includes a sensor module defining a nose, the sensor module including a sensor for sampling contaminants in the atmosphere. A processing and sending module includes processing electronics in communication with the sensor for receiving a signal from the sensor representative of sampled contaminants in the atmosphere. The processing and sending module further includes a radio frequency transmitter operably coupled to the processing electronics for transmitting a radio frequency signal representative of one or more contaminants sensed by the sensor. In another aspect, a modular air sampling system includes a sensor module containing the sensor, processing electronics, and radio frequency transmitter within the sensor module housing.

CROSS REFERENCE TO RELATED APPLICATION

This application claims priority to U.S. provisional application No.62/022,487 filed Jul. 9, 2014, which is incorporated herein by referencein its entirety.

INCORPORATION BY REFERENCE

This application is also related to U.S. Provisional Application No.61/638,368 filed Apr. 25, 2012, and U.S. Nonprovisional application Ser.No. 13/870,340 filed Apr. 25, 2013. Each of the aforementionedapplications is incorporated herein by reference in its entirety.

BACKGROUND

The present disclosure relates generally to a projectile system andmethod for detecting gaseous materials present in the atmosphere at aremote location. The present system and method find particular utilityin sensing chemical and/or biological threats in atmospheric air atspecific distances or locations for tactical or military defensepurposes. It will be recognized, however, that the present developmentmay also be used to identify and provide distance and locationinformation for chemical or biological hazards in connection withnatural disasters, industrial spills, leaks, or accidents, and so forth.One advantage of the present system resides in its ability to identifypotential chemical or biological hazards from a remote location, thusallowing the user to best plan for use of protective equipment that theuser may have at his or her disposal, such as respirator masks,self-contained breathing apparatuses, protective clothing, etc. Inpreferred embodiments, the environmental hazard sensing projectilesystem herein can be adapted for firing from preexisting launchplatforms, thus reducing costs and facilitating deployment.

SUMMARY

In one aspect, a modular projectile system comprises a chemical and/orbiological sensing module defining a nose of the projectile. A flightcontrol module is removably attachable to the sensor module and includesa plurality of airfoils, the airfoils being moveable between a refractedstate and an extended state. A processing module is removably attachedto the flight control module for receiving the sensor data from thesensor module and transmitting sensed chemical or biological hazardinformation cross-referenced with flight time and/or geolocationinformation to a radio receiver or communication network associated withthe user. A rocket module is attached to the processing module andincludes a rocket motor configured to propel the modular projectilesystem. A cartridge module is provided, which includes a charge ofexplosive material to propel the projectile system out of a launch tubeor barrel of the launch platform.

In another aspect, a modular projectile system comprises a unitary orcombined chemical and/or biological sensing and processing module whichis configured to be attached to a cartridge module with or without arocket motor.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention may take form in various components and arrangements ofcomponents, and in various steps and arrangements of steps. The drawingsare only for purposes of illustrating preferred embodiments and are notto be construed as limiting the invention.

FIG. 1 is an isometric view of a modular projectile system in accordancewith a first exemplary embodiment of the present disclosure, wherein thewings appear in the folded position.

FIG. 2 is an isometric exploded view of the modular projectile systemappearing in FIG. 1.

FIG. 3 is an exploded side elevational view of the modular projectilesystem appearing in FIG. 1.

FIG. 4 is a side elevational view of the modular projectile systemappearing in FIG. 1, wherein the housing of the sensor module isremoved, illustrating the dual air duct design of the preferredembodiment.

FIG. 5 is a block diagram of the embodiment appearing in FIG. 1.

FIG. 6 is an isometric view of a modular projectile system in accordancewith a second exemplary embodiment.

FIG. 7 is an exploded side elevational view of the modular projectilesystem appearing in FIG. 6.

FIG. 8 is a block diagram of the embodiment appearing in FIG. 6.

FIG. 9 illustrates the projectile system of FIG. 6 with a launchplatform.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Referring now to FIGS. 1-5, there is shown an exemplary modular airsampling system 100, which includes a sensor module A, a flight controlmodule B, a processing and sending module C, a motor or rocket boostermodule D, and a cartridge shell E.

The sensor module A includes a generally rounded, conical or otherwisetapered outer shell construction 10 shaped to minimize aerodynamicresistance and defining a nose cone of the rocket system 100. The sensormodule A includes an interior cavity or compartment 11 housing one ormore chemical or biological sensors 12. Such sensors includeelectrochemical sensors, metal oxide semiconductor sensors,spectroscopic gas sensors, and so forth. The one or more sensors 12 mayinclude an array of sensors configured to detect a broad range ofbiological and/or chemical contaminants. Alternatively, the sensor(s) 12could be configured to sense a one or a limited number of biologicaland/or chemical contaminants. For example, a system could be providedwith a plurality of different sensor modules A each having differentsensing capabilities, wherein the sensor module A can be selected for aparticular application based on a biological or chemical contaminantthat is expected in a given area or situation.

The sensor module A includes a pair of air intake ducts 14. The ducts 14are disposed on opposite sides of the module A. Each duct 14 includes anadjacent air flow directing surface 16. The air flow directing surfaces16 may have an airfoil-like shape and are configured to direct a flow ofair through the ducts 14 and into the interior compartment of the sensormodule A where it impinges on the one or more sensors 12. The air flowdirecting surfaces 16 may configured as a so-called submerged inlet,NACA duct or NACA scoop, or other low drag air inlet configured to allowair to flow into the ducts 14 where it contacts the one or more sensors12.

The module A includes a rear connector 19 which is complementary withand removably attachable to a forward facing connector 21 on the flightcontrol module B. The rear connector 19 and the forward connector 21 mayinclude complementary and aligned facing surfaces. In the illustratedembodiment, the rear connector 19 includes keyed projections 23 whichare received in complementary openings, channels or grooves (see FIG. 3)to allow the units A, B to be inserted and then twisted into the lockedposition. Other bayonet or keyed connections are contemplated. Incertain embodiments, markings or indicia may be provided on adjacentmodules to show proper alignment as described in the aforementionedcommonly owned U.S. application Ser. No. 13/870,340.

In certain embodiments, an electrical interface is provided within theforward and rear connectors 19, 21 to provide a conductive pathway forsending an electrical signal to a processing unit 27 in the processingand sending module C when the modules A, B, and C are connectedproperly. The electrical connections between adjacent attached membersmay also be provided to ensure that a given rocket construction preparedusing the present modular components comprises a proper configuration ofmodules. In a preferred embodiment, the electrical connections betweenthe adjacent modules serve as an interlock mechanism preventing thesystem 14 from booting up unless the attached components are properlyattached and in a proper configuration. Alternatively, or in addition,the keyed projections 23 and receptacles 25 on the connecting ends ofeach module may be keyed with distinct geometry to inhibit the improperattachment or combination of modules.

The flight control module B includes a generally cylindrical outer shellhousing 34 receiving a plurality of airfoils or wings 36circumferentially spaced about the flight control module B. The wings 36can be folded into receptacles 38 in the body of the flight controlmodule B to allow the assembled system 100 to fit into a launchplatform, which is discussed below, prior to launch of the unit 100. Asseen in FIG. 1, when the wings 36 are in the folded state, the wings 36are received in the openings 38 in the body of the module B.

The flight control module B may also include a positioning system 18,which may be an absolute or relative positioning system. Exemplarypositioning systems include, for example, a navigational system, such asGlobal Positioning System (GPS) based systems, Global NavigationSatellite System (GLONASS) based systems, etc., inertial systems, etc.In alternative embodiments, the positioning system 18 may employ a clockto record time of flight. In this manner, the relative position of theunit 100, e.g., the distance from the user at a given time, can becalculated based on time of flight and known trajectory or ballisticcharacteristics of the unit 100. In still further embodiments, thepositioning system 18 may include an accelerometer provided to count thenumber of axial rotations of the unit 100 during flight, wherein thedistance of the unit 100 from the user at a given time can be calculatedbased on the number of rotations and known trajectory or ballisticcharacteristics of the unit 100. In certain embodiments, the flightcontrol module B also includes a guidance control computer or processor20 for guiding the rocket system along a programmed fight path.

In certain embodiments, the flight control module B includes a flightcontrol processor 20 and an associated electronic memory operablycoupled thereto for storage and execution of flight control instructionsor algorithms.

After firing, the wings 36 can be moved to their extended position, asshown in the broken lines appearing in FIG. 1. Each of the wings 36 isindependently controllable and may be rotated or tilted as ailerons toprovide maneuverability/steering control as well as stability of thesensing system during flight. The wings 36 are small enough to fitwithin the housing shell 34 to allow the system 100 to fit within theconstraints of the launching platform while providing the ability toallow the system 100 to perform banking and turning maneuvers duringflight and, in preferred embodiments, are large enough to steer therocket system 100 around obstacles during flight. Additionally oralternatively, the system 100 may be maneuvered by a conventional thrustvector control system, e.g., of the type using a gimbaled booster nozzleto steer the weapon. The wings 36 may be actuated and controlled viasprings, hydraulics, pneumatics, motors, and so forth.

The processing/sending module C houses the processing unit 29 and aradio frequency (RF) transmitter or transceiver 45 and includes an outershell 44, a front connector 46 for removable attachment to a rearconnector 48 of the flight control module B, and a rear connector 50 forconnection to a front connector 52 of the booster module D. The mannerof connection may be generally as detailed above, and the connectors mayin include the projections 23 and complementary receivers 25 as detailedabove, although the geometry of the connection may be different to avoidattaching the modules improperly, e.g., in terms of sequence orcompatibility.

Electrical connections are provided between the attached modules A, B,and C for transmission of data to the RF transmitter/transceiver 45. Theprocessor 20 receives raw sensor data from the sensor 12, which can becorrelated with positional data from the positioning system 18 (oralternatively time of flight or spin count data) to identify thepresence (and optionally concentration) of an identified airborne hazardand to provide a signal representative of the same correlated toposition and/or distance from the user. The position- and/ordistance-correlated contaminant data is transmitted via the transmitter45 to an RF receiver associated with the user. In certain embodiments,the RF receiver may be a radio frequency receiver contained within alife support unit. The received data may be output to a human viewabledisplay. Information concerning the identity and position/distance ofairborne hazards allows the user to best use the breathing devices athis or her disposal.

The housing shells, wings, vanes, etc., of the present system may beformed of a metal or metal alloy material or a composite materialcomprising a fiber reinforced polymer material as are known in theaerospace industry.

The rocket booster module D includes an outer shell housing 58 defininga rocket motor configured with a rocket-based propulsion system 60 aswould be generally known in the art. The rocket motor 60 may be poweredby any suitable rocket fuel in any suitable form, including solid,liquid, gel, or any combination thereof. In certain embodiments, aplurality of retractable air vanes or fins 62 are folded intoreceptacles 64 in the housing shell 58 and are extended for stabilityduring flight. In certain embodiments or configurations, the rocketmodule D may be provided with fixed vanes or fins.

In certain embodiments, the rocket system 100 may be configured to befired from a standard or conventional launch platform, such as a grenadelauncher 250 (see FIG. 9), e.g., a single shot 40 mm grenade launcher.The rearward end 66 of the motor module D is received within a 40 mmshell casing or cartridge E, which includes a charge of explosivematerial to propel the rocket system 100 out of the launch tube of thelaunch platform. In certain embodiments, the charge may be relativelysmall, since for rocket boosted configurations it is only necessary tolaunch the rocket system 100 a sufficient distance away from theoperator to safely fire the rocket motor D. In alternative embodiments,the rocket motor may be omitted and a larger charge of explosivematerial in the cartridge E may be used.

In preferred embodiments, the launch platform is an M320 grenadelauncher module, although it will be recognized that the present systemmay be adapted for use with other calibers and/or launch platforms,including shoulder fired, stationary, etc.

FIGS. 6-8 illustrate an alternative embodiment sensing projectile system200 wherein the sensor module 10 of the sensor module A as describedabove, and the position and/or timing module 18 of the flight controlmodule B as described above, and the processor 27 and RF transmitter 45of the processing/sending unit C as described above are combined into asingle module F, wherein the above described hardware modules are withina single housing 70. The module F is attached to shell cartridge orcasing G, such as a 40 mm cartridge casing or shell. The casing Gdiffers from that casing E described above by way of the system 100 inthat the casing F is configured to contain a larger explosive charge, inthat the charge needs to be sufficient to launch the sensing projectilesystem 200 to the desired remote location where air sampling is desiredto occur.

Referring now to FIG. 9, there is shown a grenade launcher 250. Thesensing systems 100, 200 herein are advantageous in that they can beadapted for use with an existing launch platform, such as grenadelauncher 250. Advantageously, the grenade launcher 250 is based on theM320 platform and preferably the Heckler & Koch HK M320. However, it isalso contemplated that the modular air sampling system of thisdisclosure could be adapted for use with other standard launch platformsor with a custom or dedicated launch platform. In certain embodimentshaving retractable wings, such as the steering wings 36 or thestabilizing wings 62, a safety interlock may be provided for preventingmovement of said wings to the extended state when the modular airsampling system is received in a launch platform.

The invention has been described with reference to the preferredembodiments. Obviously, modifications and alterations will occur toothers upon reading and understanding the preceding detaileddescription. It is intended that the invention be construed as includingall such modifications and alterations.

What is claimed is:
 1. A modular air sampling system, comprising: asensor module defining a nose, said sensor module including a sensor forsampling contaminants in the atmosphere; a processing and sending moduleincluding processing electronics in communication with the sensor forreceiving a signal from the sensor representative of sampledcontaminants in the atmosphere, said processing and sending modulefurther including a radio frequency transmitter operably coupled to theprocessing electronics for transmitting a radio frequency signalrepresentative of one or more contaminants sensed by the sensor; and ashell casing and a propelling charge contained within the shell casingfor firing the modular air sampling system.
 2. The modular air samplingsystem of claim 1, wherein the sensor module includes a housing, saidhousing including one or more inlets allowing ambient air to pass intothe interior of the housing.
 3. The modular air sampling system of claim1, further comprising one or more air directing surfaces for directingambient air into each of the one or more inlets.
 4. The modular airsampling system of claim 1, further comprising a flight control moduleattached to the sensor module and containing a flight control system forguiding said air sampling system toward a target.
 5. The modular airsampling system of claim 4, further comprising: said flight controlmodule removably attachable to the sensor module; and said flightcontrol module including a plurality of airfoils, said airfoils beingmoveable between a retracted state and an extended state.
 6. The modularair sampling system of claim 4, further comprising a rocket moduleattached to the processing and sending module, said rocket moduleincluding a rocket motor configured to propel the modular air samplingsystem.
 7. The modular air sampling system of claim 4, furthercomprising: one or both of a position sensor and a time-of-flight sensorreceived within the flight control module and operatively coupled to theprocessing electronics, said processing electronics configured tocorrelate one or both of a time and a geographic location with thesignal from the sensor representative of sampled contaminants in theatmosphere.
 8. The modular air sampling system of claim 4 furthercomprising a data bus received within the flight control module forcommunicating sensor data to the processing electronics.
 9. The modularair sampling system of claim 1, further comprising: one or both of aposition sensor and a time-of-flight sensor operatively coupled to theprocessing electronics, said processing electronics configured tocorrelate one or both of a time and a geographic location with thesignal from the sensor representative of sampled contaminants in theatmosphere.
 10. The modular air sampling system of claim 1, furthercomprising a rocket module attached to the processing and sendingmodule, said rocket module including a rocket motor configured to propelthe air sampling system.
 11. The modular air sampling system of claim10, wherein the rocket module includes a plurality of vanes forproviding stability during flight.
 12. The modular air sampling systemof claim 10, wherein said rocket motor is powered by a rocket fuelmaterial in a form selected from the group consisting of a solid, aliquid, a gel, or any combination thereof.
 13. The modular air samplingsystem of claim 10, wherein the rocket module is removably attached tothe processing and sending module.
 14. The modular air sampling systemof claim 10, further comprising: said shell casing attached to arearward end of the rocket module, said shell casing including a chargeof explosive material configured to propel the modular air samplingsystem a distance prior to said rocket motor being fired.
 15. Themodular air sampling system of claim 14, wherein said shell casing is a40 mm shell casing.
 16. The modular air sampling system of claim 1,wherein the modular air sampling system is configured to fit into aconventional launch platform from which the modular air sampling systemcan be launched.
 17. The modular air sampling system of claim 16,wherein the launch platform is a grenade launcher.
 18. The modular airsampling system of claim 1, further comprising a launch platform forfiring the modular air sampling system.
 19. The modular air samplingsystem of claim 18, wherein the launch platform is a grenade launcher.20. The modular air sampling system of claim 1, wherein the signalrepresentative of sampled contaminants in the atmosphere is furtherrepresentative of a concentration of the sampled contaminants in theatmosphere.
 21. The modular air sampling system of claim 1, wherein thecontaminants are selected from chemical contaminants and biologicalcontaminants.
 22. A modular air sampling system, comprising: a sensormodule having a housing, said sensor module including a sensor forsampling contaminants in the atmosphere; processing electronics receivedwithin the housing in communication with the sensor for receiving asignal from the sensor representative of sampled contaminants in theatmosphere; a radio frequency transmitter received within the housingand operably coupled to the processing electronics for transmitting aradio frequency signal representative of one or more contaminants sensedby the sensor; and a shell casing and a propelling charge containedwithin the shell casing for firing the modular air sampling system. 23.The modular air sampling system of claim 22, wherein the housingincludes one or more inlets allowing ambient air to pass into theinterior of the housing.
 24. The modular air sampling system of claim23, further comprising one or more air directing surfaces for directingambient air into each of the one or more inlets.
 25. The modular airsampling system of claim 22, further comprising: one or both of aposition sensor and a time-of-flight sensor received within the housingand operatively coupled to the processing electronics, said processingelectronics configured to correlate one or both of a time and ageographic location with the signal from the sensor representative ofsampled contaminants in the atmosphere.
 26. The modular air samplingsystem of claim 22, wherein the rocket module is removably attached tothe processing and sending module.
 27. The modular air sampling systemof claim 22, further comprising: said shell casing attached to arearward end of the sensor module, said shell casing including a chargeof explosive material configured to propel the modular air samplingsystem a distance to a remote location to be sampled.
 28. The modularair sampling system of claim 27, wherein said shell casing is a 40 mmshell casing.
 29. The modular air sampling system of claim 22, whereinthe modular air sampling system is configured to fit into a conventionallaunch platform from which the modular air sampling system can belaunched.
 30. The modular air sampling system of claim 29, wherein thelaunch platform is a grenade launcher.
 31. The modular air samplingsystem of claim 22, further comprising a launch platform for firing themodular air sampling system.
 32. The modular air sampling system ofclaim 31, wherein the launch platform is a grenade launcher.
 33. Themodular air sampling system of claim 22, wherein the signalrepresentative of sampled contaminants in the atmosphere is furtherrepresentative of a concentration of the sampled contaminants in theatmosphere.
 34. The modular air sampling system of claim 22, wherein thecontaminants are selected from chemical contaminants and biologicalcontaminants.
 35. A modular air sampling system, comprising: a sensormodule defining a nose, said sensor module including a sensor forsampling contaminants in the atmosphere; a flight control moduleremovably attached to the sensor module and containing a flight controlsystem for guiding said air sampling system toward a target; and aprocessing and sending module removably attached to the flight controlmodule, the processing and sending module including processingelectronics in communication with the sensor for receiving a signal fromthe sensor representative of sampled contaminants in the atmosphere,said processing and sending module further including a radio frequencytransmitter operably coupled to the processing electronics fortransmitting a radio frequency signal representative of one or morecontaminants sensed by the sensor.
 36. The modular air sampling systemof claim 35, wherein said flight control module includes a plurality ofairfoils, said airfoils being moveable between a retracted state and anextended state.